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millibars on the baro counter. The altimeter provides the following
displays:
- Counter drum display of altitude, marked in 20-foot increments
- Pointer display of altitude between thousand-foot levels with 20-foot
graduations.
Altitudes below 10,000 feet are indicated by a black and white Crosshatch
on the left digit position of the counter display.
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OPERATING MANUAL
COURSE 1 KNOB
Sets course pointer and course digital read-out on
pilot's HSI to the desired course.
COURSE 2 KNOB
Sets course pointer and course digital read-out on
copilot's HSI to the desired course.
HEADING KNOB
Sets heading bugs on pilot's and copilot's HSI to the
desired heading.
Instrument Remote Controller
Figure 5
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OPERATING MANUAL
ALTITUDE
POINTER
BAROMETRIC PRESSURE
SET KNOB
ALTITUDE DISPLAY
BAROMETRIC PRESSURE
Altimeter
Figure 6
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OPERATING MANUAL
(1) Altitude Alert
The altitude alert annunciator light comes on to provide a visual
indication when the aircraft is within 1000 feet of the preselected
altitude during the capture manoeuvre and goes out when the aircraft
is within 250 feet from the preselected altitude. After capture, the
light comes on if the aircraft departs more than 250 feet from the
selected altitude, and goes out when the aircraft has departed more
than 1000 feet from the selected altitude. A momentary audio alert is
also provided when the aircraft is within 1000 feet of the preselected
altitude or has departed 250 feet from the selected altitude after
capture.
(2) Failure Warning Flag
An internal failure monitor controls a failure warning flag which
indicates power loss or data invalid.
Pilot's Vertical Speed Indicator (Figure 7)
The pilot's vertical speed indicator provides a servo-driven pointer
display of vertical speed. Vertical speed rates from 0 to +6000 feet per
minute are displayed on the indicator.
Pilot's Mach/Airspeed Indicator (Figure 8)
The pilot's Mach/airspeed indicator is a totally servo-driven instrument
with a counter display of Mach and pointer displays of airspeed and maximum
operating airspeed (Vmo) as computed in the air data computer.
TAS/SAT/TAT Indicator (Figure 9)
The combined true airspeed, static air temperature/total air temperature
indicator provides and incandescent digital display of both TAS and SAT or
TAT signals as generated by the air data computer.
VNAV Computer/Controller (Figure 10)
The VNAV computer/controller (VNCC) provides data insertions and displays
for altitude alerting, altitude preselect and VNAV modes. In operation,
the pilot enters data by turning the display selector switch to the desired
position and slewing with the set knob. The slew speed is proportional to
the amount of rotation of the knob.
(1) Altitude Preselect
The altitude is selected by placing the selector switch to ALT and
slewing to the desired value. No further action is taken on the
VNCC. To initiate altitude preselect, the ALTSEL switch/light is
selected on the flight director mode selector.
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OPERATING MANUAL
Altitude Alert
As the aircraft reaches a point 1,000 feet from the selected altitude,
the light on the altimeter comes on and the warning horn sounds for 1
second. The light remains on until the aircraft is 250 feet from the
selected altitude. If the aircraft now deviates by 250 feet from the
selected altitude, the light comes on again and the horn sounds . The
light remains on until the aircraft returns to within 250 feet of the
selected altitude or a new altitude is set, which resets the alert
horn and light.
Vertical Navigation Computation
The use the VNAV computation capability of the VNCC, the pilot must
set the station elevation, bias distance and vertical angle after
selecting the desired altitude. This is accomplished as follows:
(a) The station elevation, STAEL, position is selected and the
station elevation is set on the display by rotating the set
knob. Resolution is 100 feet.
(b) The TO or FR position is selected and the distance ahead of or
beyond the NAVAID (alongtrack offset) is set. Resolution is 0.1
nautical mile.
(c) The vertical angle, VANG, position is selected and the computed
vertical path angle to the desired destination is displayed. The
pilot may observe the continuously computed flight path angle
(angle compute mode) until the desired angle is displayed, and
　
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